Rohr, Inc.

Timothy Gormley

Jihad I Ramlaoui

Imad D Ghandour

Stephane Dion

Radhakrishna Chilukuri

Erik Linde

Jasen Miner

Luis A Lopez

Duffy Adam Randolph

Vincent Vignoboul

Timothy Repp

Erik N Linde

An assembly for an aircraft propulsion system includes a fixed structure, a translating structure and a thrust reverser. The thrust reverser includes a blocker door, a structure link and a door link. The blocker door is pivotally coupled to the translating structure. The structure link includes a first structure link arm, a second structure link arm and a structure link mount connected to the first structure link arm and the second structure link arm. The first structure link arm and the second structure link arm are each pivotally coupled to the fixed structure. The first structure link arm and the second structure link arm laterally converge towards one another as the first structure link arm and the second structure link arm extend longitudinally towards the structure link mount. The door link extends longitudinally between and is pivotally coupled to the structure link mount and the blocker door.

Thrust reverser with blocker door folding linkage

An assembly is for an aircraft propulsion system. This assembly includes a fixed structure, a translating structure and a thrust reverser. The translating structure is configured to translate between a stowed position and a deployed position. The thrust reverser includes a blocker door, a linkage mount and an actuation linkage. The blocker door is pivotally coupled to the translating structure. The linkage mount includes a mount link, a mount spring and a mount stop. The mount link is pivotally coupled to the fixed structure about a pivot axis. The mount spring is configured to bias the mount link about the pivot axis against the mount stop. The actuation linkage operatively couples the blocker door to the mount link.

Thrust reverser with lost motion device

An assembly is provided for an aircraft propulsion system. This assembly includes a fixed structure, a translating structure and a thrust reverser. The translating structure is configured to translate between a stowed position and a deployed position. The thrust reverser includes a blocker door, an actuation linkage and a door lock. The blocker door is pivotally coupled to the translating structure. The actuation linkage operatively couples the blocker door to the fixed structure such that translation of the translating structure to the deployed position actuates pivoting of the blocker door into a flowpath. The door lock is configured to lock the actuation linkage to the translating structure such that the pivoting of the blocker door into the flowpath is delayed as the translating structure translates from the stowed position towards the deployed position.

Thrust reverser with blocker door lock

An assembly for an aircraft propulsion system includes a fixed structure, a translating structure and a thrust reverser. The thrust reverser includes a blocker door, a door link and a structure link. The blocker door is pivotally coupled to the translating structure. The door link includes a first door link arm, a second door link arm and a door link mount connected to the first door link arm and the second door link arm. The first door link arm and the second door link arm are each pivotally coupled to the blocker door. The first door link arm and the second door link arm laterally converge towards one another as the first door link arm and the second door link arm extend longitudinally towards the door link mount. The structure link extends longitudinally between and is pivotally coupled to the door link mount and the fixed structure.

An assembly for an aircraft propulsion system includes a translating structure and a thrust reverser. The thrust reverser includes a blocker door, an actuation linkage and a fairing. The blocker door is pivotally coupled to the translating structure. The blocker door includes a door surface and a channel projecting into the blocker door from the door surface. The door surface forms an outer peripheral boundary of a flowpath when the translating structure is stowed. The door surface projects into the flowpath when the translating structure is deployed. The actuation linkage is pivotally coupled to the blocker door. The actuation linkage is disposed in the channel when the translating structure stowed. The fairing projects away from the door surface into the flowpath. The fairing forms an aerodynamic cover over the channel when the translating structure is stowed.

Thrust reverser blocker door with fairing

A thrust reverser for an aircraft propulsion system includes a fixed thrust reverser structure including a wall, a sleeve configured to translate between a first stowed position and a second position, and a blocker door assembly including a plurality of blocker doors. An upstream end of the sleeve is disposed at the wall with the translating sleeve in the first stowed position. A locking assembly includes a locking body and a receiver. Each blocker door includes a body pivotably mounted to the sleeve by a hinge and the locking body. Translation of the sleeve from the first to the second position effects pivoting of the blocker door body from a first stowed position to a second position. In a locked position, the locking body is engaged with the wall and disposed at the receiver. In an unlocked position, the locking body is disengaged with the wall and the receiver.

Locking assembly for an aircraft propulsion system thrust reverser

An apparatus is provided for an aircraft propulsion system. This apparatus includes a pivoting door thrust reverser system, and the pivoting door thrust reverser system includes a plurality of thrust reverser doors. Each of the thrust reverser doors is configured to pivot about a respective pivot axis between a stowed position and a deployed position. The thrust reverser doors include a first thrust reverser door and a second thrust reverser door. The second thrust reverser door is arranged to an opposing side of the pivoting door thrust reverser system from the first thrust reverser door. The pivot axis of the first thrust reverser door is angularly offset from a reference line by an acute angle. The reference line is coincident with and perpendicular to a centerline of the pivoting door thrust reverser system.

Thrust reverser system with angled door pivot axes

An assembly is provided for an aircraft propulsion system. This assembly includes a center body, a scarfed inlet structure and an inlet passage. The scarfed inlet structure extends circumferentially about the center body. The inlet passage is radially between and formed by at least the center body and the scarfed inlet structure. A first component of the assembly is configured to rotate about an axis relative to a second component of the assembly between: (A) a first position where a metering portion of the inlet passage has a first area; and (B) a second position where the metering portion has a second area. The first component is one of the center body or the scarfed inlet structure, and the second component is the other one of the center body or the scarfed inlet structure.

Aircraft propulsion system with variable area inlet assembly

A nacelle system having a translating structure is disclosed. In various embodiments, the nacelle system includes a fixed structure; a thrust reverser having a translating sleeve configured to translate relative to the fixed structure and in response to a first dual-circuit hydraulic system; and a variable area fan nozzle having a translating nozzle configured to translate relative to the translating sleeve and in response to a second dual-circuit hydraulic system.

Drive system for translating structure

An assembly is provided for an aircraft propulsion system. This aircraft propulsion system assembly includes a nacelle inlet structure. The nacelle inlet structure includes an inner inlet opening, an outer inlet opening and a rotating structure. The rotating structure extends circumferentially about the inner inlet opening. The rotating structure is configured to rotate about an axis between a first position and a second position. The rotating structure at least partially closes the outer inlet opening in the first position. The rotating structure at least partially opens the outer inlet opening in the second position.

Aircraft propulsion system inlet structure with variable airflow inlet area

A variable area nozzle assembly for a gas turbine engine includes a nozzle disposed about a nozzle centerline and a fixed ring radially surrounding the nozzle. The nozzle includes a radially outer surface and a radially inner surface. The radially inner surface defines an outlet cross-sectional area of the nozzle. The nozzle is movable relative to the nozzle centerline between a first position of the radially inner surface defining a maximum area of the outlet cross-sectional area and a second position of the radially inner surface defining a minimum area of the outlet cross-sectional area. With the nozzle in the first position, the radially outer surface contacts the fixed ring. With the nozzle in the second position, the radially outer surface is spaced from the fixed ring.

Variable area nozzle and method for operating same

A nacelle may comprise a fixed structure and a translating structure configured to translate relative to the fixed structure. A first drive system may be operationally coupled to the translating structure. The drive system may comprise a primary actuator coupled to the fixed structure and including a primary rod and a primary gear rotationally coupled to the primary rod, a torque shaft rotationally coupled to the primary gear, and a secondary actuator operationally coupled to the primary actuator via the torque shaft.

A thrust reverser includes a frame, a track disposed on the frame, a carrier operatively coupled to the track, and a first reverser door operatively coupled to the carrier. The first reverser door is movable relative to the frame. The first reverser door is configured to move to a first position in response to the carrier moving with respect to the track in a first direction, and move to a second position in response to the carrier moving with respect to the track in a second direction.

Thrust reverser single degree of freedom actuator mechanism systems and methods

A thrust reverser may include a frame, an actuation arrangement, a reverser door pivotally coupled to the frame, and a deployable fairing pivotally coupled to the frame, wherein the deployable fairing is configured to move away from a central axis of the thrust reverser to provide clearance for one of more thrust reverser pivot doors to rotate into a deployed position.

Deployable fairing for door reversers systems and methods

A method for deploying a thrust reverser includes translating a carrier along a track, transferring a first load between the carrier and a first reverser door in response to the carrier translating along the track, rotating the first reverser door between a closed position and an open position in response to the carrier translating along the track, transferring a second load between the carrier and a deployable fairing in response to the carrier translating along the track, and rotating the deployable fairing between a stowed position and a deployed position in response to the carrier translating along the track.

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Bonita, CA, United States of America

Timothy Gormley